GB2074655A - Particle separator for the inlet of a gas turbine engine - Google Patents

Particle separator for the inlet of a gas turbine engine Download PDF

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Publication number
GB2074655A
GB2074655A GB8013020A GB8013020A GB2074655A GB 2074655 A GB2074655 A GB 2074655A GB 8013020 A GB8013020 A GB 8013020A GB 8013020 A GB8013020 A GB 8013020A GB 2074655 A GB2074655 A GB 2074655A
Authority
GB
United Kingdom
Prior art keywords
duct
door
plenum
air
particle separator
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
GB8013020A
Other versions
GB2074655B (en
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Avco Corp
Original Assignee
Avco Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Avco Corp filed Critical Avco Corp
Publication of GB2074655A publication Critical patent/GB2074655A/en
Application granted granted Critical
Publication of GB2074655B publication Critical patent/GB2074655B/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
    • F02C7/052—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with dust-separation devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0246—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising particle separators
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Separating Particles In Gases By Inertia (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
  • Cyclones (AREA)

Abstract

A duct 6 is constructed on a nacelle 2 in which the engine 1 is mounted. Air flows into the engine intake plenum 4 via an opening 16 in duct wall 17. A swingable door 9 is mounted at the opening and is movable by actuator 11 from a first position where it partially blocks the opening to a second position, shown, where it blocks the outlet 8 of the duct. In the first position the door causes airflow entering the plenum to bend, hence giving rise to inertial separation of undesired air contaminants. In the second position air entering the duct 6 by the inlet 7 is fed to the plenum, giving a ram air effect. <IMAGE>

Description

1
GB 2 074 655 A 1
SPECIFICATION
Particle separator system for the inlet of a gas turbine engine
65
The present invention relates to a particle 5 separator system for the inlet of a gas turbine 70
engine.
The functioning of a gas turbine engine depends on a continuous flow of a large volume of air through the engine. Since some components of 10 the engine, for example, the compressor rotor, are 75 rotating at extremely high speed any contaminants in the airflow will have a destructive effect on engine performance. Particles, such as super-cooled water droplets, impinging on the 15 rotor may cause an imbalance and an eventual 80 disintegration because of the high forces involved.
It is, therefore, essential that some means is employed to separate out contaminants from the airflow entering the engine plenum. In the past, a 20 great variety of barrier filters were employed; 85
however, these filters had the disadvantage of encouraging the formation of ice in the inlet which can eventually block the inlet and prevent the flow of air into the engine.
25 Inertia! separator devices have been used to 90 divide the particles of heavier mass in the inlet airflow away from the engine intake through a bypass duct. Atypical system of this type is described in U.S. Patent No. 3329377 which 30 issued on July 4,1967. In this system a hinged 95 deflecting vane is placed in the inlet duct upstream of the intake to the engine plenum. The vane extends into the duct restricting the airflow. The airflow is caused to accelerate and turn 35 through a substantial angle around the deflecting 100 vane. Particles of heavier mass cannot make the turn and are exhausted through a by-pass duct. The hinged nature of the vane allows the adjustment of the ratio of air by-passed. Since the 40 deflecting vane is attached to the wall upstream of 105 the entrance to the engine plenum, it is always in the way of the airflow even at full retraction. This results in a pressure loss end prevents maximum ram air operation, resulting in an unnecessary 45 limitation of engine performance. 110
According to a first aspect of the present invention there is provided a particle separator system for the inlet of a gas turbine engine in which the intake plenum of the engine is fed from 50 a duct via an opening in a wall of the duct, the 115 duct having an inlet and outlet for the flow of air therethrough, wherein a door is mounted at the opening and is movable from a first position to a second position, such that, in use, when the door 55 is in the first position, air entering the plenum from 120 the duct must bend through a substantial angle, and when the door is in the second position it substantially blocks off the outlet, thereby to cause air entering the duct to pass into the 60 plenum. 125
According to a further aspect of the present invention there is provided an assembly comprising a gas turbine engine mounted in a nacelle, a duct having an opening for feeding air to the intake plenum of the engine, and a particle separator system as defined above.
According to yet another aspect there is provided a particle separator system for the inlet of a gas turbine engine which is enclosed in a nacelle of an aircraft comprising:
a longitudinally extending duct formed on the outside of the nacelle, the duct having an inlet and an outlet to allow for the flow of air therethrough, an opening in an interior wall of the duct adjacent to the nacelle, said opening connecting the intake plenum of the gas turbine engine with the duct, thereby to form an entrance for the flow of air into the plenum from the duct; a door mounted at the said entrance and movable between a first position and second position, such that in the first position the door extends partially across the said entrance so that in use the airflow entering the plenum bends through a substantial angle, and in the second position the door blocks the outlet so that in use substantially all of the air entering the duct flows into the plenum; and actuating means operatively associated with the door to move said door between the first and second positions.
In a particular embodiment for use with aircraft, the inlet duct extends axially along the nacelle of the gas turbine engine beginning with a forward facing entrance or inlet and terminating in a rearward facing exit or outlet. In the intermediate portion of the duct an opening is formed which communicates with the engine plenum. The entrance is constructed to allow the flow of a high volume of air during periods which require high performance. A swingable door is mounted at the entrance to the plenum on a lever arm which is pivotally connected to the engine structure. An actuating mechanism is provided to swing the door from a first position where it partially closes the entrance to the plenum to a second position where it completely closes the exit portion of the duct. In the particle separation mode the door is swung into the plenum entrance. This requires the incoming airflow to bend through an increased angle before entering the engine. Particles of higher inertia, such as ice, will separate and be exhausted through the exit of the duct. When full performance is required of the gas turbine engine, the swinging door may be moved to a position where it closes the exit of the duct.
It can be seen that the use of the particle separator system of the present invention will reduce the formation of ice in a gas turbine engine • assembly and hence also be an aid to de-icing.
The invention will be further described by way of example with reference to the accompanying drawings, in which:
Fig. 1 is a drawing of the nose portion of an engine nacelle cut away to show the gas turbine engine and its inlet duct and illustrates one embodiment of the present invention.
Fig. 2 is a schematic diagram of the particle separator system of the embodiment of Fig. 1,
Fig. 3 is a schematic diagram of a second embodiment of the present invention.
Referring now to the drawings, there is shown
2
GB 2 074 655 A 2
in Fig. 1, a gas turbine engine 1 mounted and enclosed in the nose portion of an engine nacelle 2. The engine 1 is connected to drive the propeller 3 which creates the thrust moving an aircract, or 5 the like. Air is supplied to the engine through intake 4 which communicates with annular plenum 5.
An inlet duct 6 is constructed at the bottom of nacelle 2 and is defined by a scoop 15. The duct 6 10 extends axially from a forward facing inlet 7 to a rearward facing outlet 8. In the intermediate portion of the duct, an opening 16 is constructed in an interior wall of the duct on the nacelle 2 to provide an entrance for incoming airflow to the 15 engine plenum 5. The entrance is formed between a curved wall portion 17 and a corner section 18. A swingable door 9 is mounted on a lever arm 10 in entrance 16. The lever arm 10 is fixed to an axle 13 which is rotatably mounted on a portion of the 20 engine support structure (not shown). Rotation of axle 13 will move door 9 from a first position, as shown in Fig. 2, to a second position, as shown by phantom lines 19 in Fig. 2.
The door 9 is shaped to form an extension of 25 curved surface 17 into the opening 16 of the plenum thereby forcing the inlet airflow to turn through a substantial angle before entering the plenum. This angle creates an inertial separation effect which divides the heavier particles in the 30 airflow to the outside of the turn. The higher inertia of these particles prevents their turning and carries them past the corner surface 18 and out of the exit 8 of duct 6. In this manner the ingestion of ice and other contaminants into the engine intake 35 is prevented or substantially reduced. Under some conditions a coating of ice may build up on corner section 18. In order to prevent this, a heater 14 may be constructed on surface 18 as shown. Heater 14 may be energized by bleeding hot 40 exhaust air from the engine.
During periods of use when particle separation is not required, or where peak performance is necessary, the swingable door 9 may be moved to the second position where it engages corner wall 45 portion 18 and extends across duct 6 to block exit 8. In this position full ram air is provided to the engine intake.
Controlled rotation of axle 13 can be obtained by employing an air cylinder 11 which may be 50 powered by engine bleed air. The piston rod 20 is connected to an operating lever 12 which in turn is fixed to axle 13. Actuation of cylinder 11 will move the swingable door 9 between its first and second positions.
55 The swingable door 9 is designed to conform to the shape of duct 6 without restricting the airflow therein. This minimizes any performance penalty which may result from the particle separator function.
60 The swinable door 9 may be constructed in the form of a flat plate, as shown in Fig. 3. This door, in the particle separation mode, will be moved to a first fixed position where it will extend into the duct to deflect the airflow through an even greater 65 angle, thereby increasing the efficiency of the separation effect. By swinging the door to its rearward second position full ram air is supplied to the engine plenum in a manner similar to the embodiment shown in Fig. 2.
In the manner described an efficient separator system is provided while allowance is made for maximum ram air during certain operations.

Claims (1)

1. A particle separator system for the inlet of a gas turbine engine which is enclosed in a nacelle of an aircraft comprising:
a longitudinally extending duct formed on the outside of the nacelle, the duct having an inlet and an outlet to allow for the flow of air therethrough, an opening in an interior wall of the duct adjacent to the nacelle, said opening connecting the intake plenum of the gas turbine engine with the duct, thereby to form an entrance for the flow of air into the plenum from the duct;
a door mounted at the said entrance and movable between a first position and second position, such that in the first position the door extends partially across the said entrance so that in use the airflow entering the plenum bends through a substantial angle; and in the second position the door blocks the outlet so that in use substantially all of the air entering the duct flows into the plenum; and actuating means operatively associated with the door to move the said door between the first and second positions.
2. A particle separator system as claimed in claim 1, wherein the door is designed to conform to the shape of the duct thereby not to restrict the flow area of the duct when in use.
3. A particle separator system as claimed in claim 1, wherein the door is designed in the form of a flat plate and is constructed to extend into the duct, so that in use it restricts the airflow in the duct immediately upstream of the plenum entrance when the door is in the said first position.
4. A particle separator system as claimed in claim 1,2 or 3, wherein the actuating means comprises:
an axle mounted for rotation in the vicinity of 5 the plenum entrance;
at least one lever arm fixed to the axle and extending into the plenum entrance to receive the door;
an air cylinder, the piston of which is operatively connected to the axle to cause rotation of the axle upon actuation of the air cylinder; and a means for supplying high pressure air to the air cylinder to control the actuation of the air cylinder.
5. A particle separator system for the inlet of a gas turbine engine in which the intake plenum of the engine is fed from a duct via an opening in a wall of the duct, the duct having an inlet and outlet for the flow of air therethrough, wherein a door is mounted at the opening and is movable from a first position to a second position, such that, in use, when the door is in the first position, air entering the plenum from the duct must bend
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GB 2 074 655 A 3
through a substantial angle, and when the door is in the second position it substantially blocks off the outlet, thereby to cause air entering the duct to pass into the plenum.
5 6. A particle separator system as claimed in claim 5, wherein the door is shaped so as to conform to the shape of the duct, thereby to avoid restriction of the flow area of the duct when in use.
10 7. A particle separator system as claimed in claim 5, wherein the door comprises a flat plate and is constructed such that it extends into the duct so that in use it restricts the airflow immediately upstream of the plenum entrance
1 5 when in the first position.
8. A particle separator system for the inlet of a gas turbine engine system, substantially as hereinbefore described with reference to Figs. 1 and 2, or Fig. 3 of the accompanying drawings.
20 9. An assembly comprising a gas turbine engine mounted in a nacelle, a duct having an opening for feeding air to the intake plenum of the engine, and a particle separator system as claimed on any of claims 5 to 8.
25 10. An aircraft including an assembly as claimed in claim 9.
11. A door for use in a system as claimed in any of claims 1 to 8.
Printed for Her Majesty's Stationery Office by the Courier Press, Leamington Spa, 1981. Published by the Patent Office, 25 Southampton Buildings, London, WC2A 1AY, from which copies may be obtained.
GB8013020A 1979-03-15 1980-04-21 Particle separator for the inlet of a gas turbine engine Expired GB2074655B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US06/021,422 US4250703A (en) 1979-03-15 1979-03-15 Swinging door particle separator and deicing system

Publications (2)

Publication Number Publication Date
GB2074655A true GB2074655A (en) 1981-11-04
GB2074655B GB2074655B (en) 1983-06-29

Family

ID=21804135

Family Applications (1)

Application Number Title Priority Date Filing Date
GB8013020A Expired GB2074655B (en) 1979-03-15 1980-04-21 Particle separator for the inlet of a gas turbine engine

Country Status (6)

Country Link
US (1) US4250703A (en)
CA (1) CA1120733A (en)
DE (1) DE3015651C2 (en)
FR (1) FR2481746A1 (en)
GB (1) GB2074655B (en)
SE (1) SE421232B (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2659690A1 (en) * 1990-03-19 1991-09-20 Gen Electric METHOD AND APPARATUS FOR EXPULTING MATERIALS FROM THE CORE FLOW PATH IN THE BYPASS FLOW PATH OF AN ENGINE.
US5279109A (en) * 1991-09-03 1994-01-18 General Electric Company Gas turbine engine variable bleed pivotal flow splitter
US8935926B2 (en) 2010-10-28 2015-01-20 United Technologies Corporation Centrifugal compressor with bleed flow splitter for a gas turbine engine
US9890711B2 (en) 2010-09-21 2018-02-13 United Technologies Corporation Gas turbine engine with bleed duct for minimum reduction of bleed flow and minimum rejection of hail during hail ingestion events

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CA1116418A (en) * 1979-07-18 1982-01-19 Pratt & Whitney Aircraft Of Canada Limited Vane fairing for inertial separator
US4397431A (en) * 1981-11-02 1983-08-09 Avco Corporation Fail-safe, anti-icing system for aircraft engines
US4713934A (en) * 1981-11-21 1987-12-22 Rolls-Royce Plc Gas turbine engine air intake
US4844382A (en) * 1983-10-19 1989-07-04 Raisbeck Engineering, Inc. Dual turning vane air inlet assembly
US4617028A (en) * 1983-11-03 1986-10-14 General Electric Company Aircraft engine air intake including a foreign object separator
US4674704A (en) * 1985-12-03 1987-06-23 The United States Of America As Represented By The Secretary Of The Air Force Direct air cooling system for airborne electronics
US4760978A (en) * 1986-11-19 1988-08-02 Cox & Company, Inc. Ice-free screen for protecting engines from damage caused by foreign bodies in the intake airstream
US5088660A (en) * 1989-08-04 1992-02-18 United Technologies Corporation Bleed stability door
US4972672A (en) * 1989-09-28 1990-11-27 Pratt & Whitney Canada, Inc. Controlled bypass inlet duct
US5284012A (en) * 1991-05-16 1994-02-08 General Electric Company Nacelle cooling and ventilation system
US5961067A (en) * 1996-09-10 1999-10-05 Allison Engine Company Method for reducing turboprop noise
US6651929B2 (en) 2001-10-29 2003-11-25 Pratt & Whitney Canada Corp. Passive cooling system for auxiliary power unit installation
DE10162238A1 (en) 2001-12-18 2003-07-10 Rolls Royce Deutschland Air intake system of a PTL drive
US6702873B2 (en) 2002-04-23 2004-03-09 The Boeing Company High particle separation efficiency system
GB0617769D0 (en) * 2006-09-09 2006-10-18 Rolls Royce Plc An engine
FR2915461B1 (en) * 2007-04-24 2009-06-05 Airbus France Sas AIR INTAKE ARRANGEMENT FOR A VEHICLE, IN PARTICULAR AN AIRCRAFT.
US8079550B2 (en) * 2008-07-18 2011-12-20 Hamilton Sundstrand Corporation Auxiliary power unit inlet door actuation mechanism
EP2379409B1 (en) 2008-12-30 2017-12-20 Sikorsky Aircraft Corporation Engine air particle separator
US8945254B2 (en) 2011-12-21 2015-02-03 General Electric Company Gas turbine engine particle separator
US9067679B2 (en) * 2011-12-30 2015-06-30 Aerospace Filtration Systems, Inc. Heated screen for air intake of aircraft engines
US8452516B1 (en) * 2012-01-31 2013-05-28 United Technologies Corporation Variable vane scheduling based on flight conditions for inclement weather
USD736089S1 (en) 2012-06-14 2015-08-11 S.C. Johnson & Son, Inc. Bottle
USD736637S1 (en) 2012-06-14 2015-08-18 S.C. Johnson & Son, Inc. Bottle
USD722879S1 (en) 2012-06-14 2015-02-24 S.C. Johnson & Son, Inc. Bottle
US9518513B2 (en) 2012-10-12 2016-12-13 General Electric Company Gas turbine engine two degree of freedom variable bleed valve for ice extraction
US9982598B2 (en) 2012-10-22 2018-05-29 General Electric Company Gas turbine engine variable bleed valve for ice extraction
US9644537B2 (en) * 2013-03-14 2017-05-09 United Technologies Corporation Free stream intake with particle separator for reverse core engine
FR3009022B1 (en) * 2013-07-23 2018-03-16 Safran Aircraft Engines INTERMEDIATE CASTER HUB FOR AIRCRAFT TURBOREACTOR COMPRISING DOORS WITH PROFILE GEOMETRY
US9394827B2 (en) 2013-08-07 2016-07-19 Honeywell International Inc. Inlet particle separator system with flow passage through hub and/or shroud
EP2957503B1 (en) 2014-06-19 2016-08-17 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Aircraft with two engines having by-pass air inlet openings and bleed air outlets as well as engine for an aircraft
US10054050B2 (en) * 2014-08-19 2018-08-21 Pratt & Whitney Canada Corp. Low noise aeroengine inlet system
US10221764B2 (en) 2014-08-19 2019-03-05 Pratt & Whitney Canada Corp. Variable geometry inlet system
US9957889B2 (en) 2014-08-19 2018-05-01 Pratt & Whitney Canada Corp. Low noise aeroengine inlet system
US9951690B2 (en) 2014-08-19 2018-04-24 Pratt & Whitney Canada Corp. Low noise aeroengine inlet system
DE102014217829A1 (en) 2014-09-05 2016-03-10 Rolls-Royce Deutschland Ltd & Co Kg Method for drawing bleed air and aircraft engine with at least one device for drawing bleed air
FR3028289B1 (en) 2014-11-06 2019-12-27 Airbus Operations (S.A.S.) AIRCRAFT TURBOMACHINE COMPRISING AN AIR INTAKE BOX WITH VARIABLE AERODYNAMIC PROFILE
GB201421773D0 (en) * 2014-12-08 2015-01-21 Rolls Royce Deutschland Air intake arrangement
US9719352B2 (en) 2014-12-17 2017-08-01 Honeywell International Inc. Compartment based inlet particle separator system
US10100734B2 (en) * 2015-02-24 2018-10-16 Honeywell International Inc. Multi-channel particle separator
US10138904B2 (en) 2016-01-06 2018-11-27 Honeywell International Inc. Inlet particle separator system with high curvature hub
USD845135S1 (en) 2017-02-24 2019-04-09 S. C. Johnson & Son, Inc. Bottle neck with cap
US11111024B2 (en) 2018-01-12 2021-09-07 Honeywell International Inc. Foldable RAM air inlet filter
US11525398B2 (en) * 2019-04-02 2022-12-13 The Boeing Company Engine inlet with deployable particle separator

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GB571281A (en) * 1942-05-01 1945-08-17 United Aircraft Corp Improvements in or relating to air ducts
US2381705A (en) * 1942-06-11 1945-08-07 Vokes Cecil Gordon Filter
US2623610A (en) * 1949-10-25 1952-12-30 Gen Electric Air inlet screen for gas turbines
US2970431A (en) * 1959-01-02 1961-02-07 Curtiss Wright Corp Rotating inlet for jet engines
US3329377A (en) * 1965-10-11 1967-07-04 United Aircraft Canada Protection for aircraft engines against snow, ice and airborne particles
US3338049A (en) * 1966-02-01 1967-08-29 Gen Electric Gas turbine engine including separator for removing extraneous matter
US3952972A (en) * 1974-12-24 1976-04-27 United Aircraft Of Canada Limited Inertial separator

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2659690A1 (en) * 1990-03-19 1991-09-20 Gen Electric METHOD AND APPARATUS FOR EXPULTING MATERIALS FROM THE CORE FLOW PATH IN THE BYPASS FLOW PATH OF AN ENGINE.
US5123240A (en) * 1990-03-19 1992-06-23 General Electric Co. Method and apparatus for ejecting foreign matter from the primary flow path of a gas turbine engine
US5279109A (en) * 1991-09-03 1994-01-18 General Electric Company Gas turbine engine variable bleed pivotal flow splitter
US9890711B2 (en) 2010-09-21 2018-02-13 United Technologies Corporation Gas turbine engine with bleed duct for minimum reduction of bleed flow and minimum rejection of hail during hail ingestion events
US8935926B2 (en) 2010-10-28 2015-01-20 United Technologies Corporation Centrifugal compressor with bleed flow splitter for a gas turbine engine

Also Published As

Publication number Publication date
GB2074655B (en) 1983-06-29
US4250703A (en) 1981-02-17
FR2481746A1 (en) 1981-11-06
DE3015651C2 (en) 1983-03-03
DE3015651A1 (en) 1981-10-29
SE8002886L (en) 1981-10-18
SE421232B (en) 1981-12-07
CA1120733A (en) 1982-03-30

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